| タイトル | Flowfield computations over the Space Shuttle Orbiter with a proposed canard at a Mach number of 5.8 and 50 degrees angle of attack |
| 著者（英） | Buning, Pieter G.; Hobson, Garth V.; Reuter, William H. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1993-01-01 |
| 言語 | eng |
| 内容記述 | An effective control canard design to provide enhanced controllability throughout the flight regime is described which uses a 3D, Navier-Stokes computational solution. The use of canard by the Space Shuttle Orbiter in both hypersonic and subsonic flight regimes can enhance its usefullness by expanding its payload carrying capability and improving its static stability. The canard produces an additional nose-up pitching moment to relax center-of-gravity constraint and alleviates the need for large, lift-destroying elevon deflections required to maintain the high angles of attack for effective hypersonic flight. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 93A23014
AIAA PAPER 93-0322 |
| 権利 | Copyright |
